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EP2746150A1 - Outer fuel tank access cover, wing and aircraft comprising such a cover - Google Patents

Outer fuel tank access cover, wing and aircraft comprising such a cover Download PDF

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Publication number
EP2746150A1
EP2746150A1 EP12382523.4A EP12382523A EP2746150A1 EP 2746150 A1 EP2746150 A1 EP 2746150A1 EP 12382523 A EP12382523 A EP 12382523A EP 2746150 A1 EP2746150 A1 EP 2746150A1
Authority
EP
European Patent Office
Prior art keywords
ftac
outer ftac
aircraft
wing
fuel tank
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12382523.4A
Other languages
German (de)
French (fr)
Other versions
EP2746150B1 (en
Inventor
Marcos Alazraki
Jose Sanz Torrijos
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SL
Original Assignee
Airbus Operations SL
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SL filed Critical Airbus Operations SL
Priority to EP12382523.4A priority Critical patent/EP2746150B1/en
Priority to EP15156088.5A priority patent/EP2902313B1/en
Priority to US14/136,725 priority patent/US20140191085A1/en
Priority to CN201310716752.3A priority patent/CN103879548A/en
Publication of EP2746150A1 publication Critical patent/EP2746150A1/en
Application granted granted Critical
Publication of EP2746150B1 publication Critical patent/EP2746150B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/02—Tanks
    • B64D37/06—Constructional adaptations thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1407—Doors; surrounding frames
    • B64C1/1446—Inspection hatches
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water

Definitions

  • the present invention describes an outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft.
  • the invention belongs to the field of designing auxiliary pieces in the wings of aircraft to control the risk of impact against an inner FTAC when an impact occurs against the outer FTAC. This impact can be caused by a tire.
  • Manholes in an aircraft provide access to the fuel tank.
  • Manholes comprise an inner fuel tank access cover (inner FTAC), an outer FTAC and a void area between the two covers.
  • Fuel Tank Access Covers (FTACs) are mechanically fastened, with fasteners, such as bolts, and clamped against the aircraft wing skin to provide fuel tank access sealing.
  • FTAC are designed to meet a wide array of requirements, some of them are: no fuel leaks, fire resistance, resistance to a tire impact, resistance to impacts resulting from an UERF (Uncontained Engine Rotor Failure), EMH/lightning strike, seal friction, and wing bending.
  • the current design approach to address the resistance of the structure to an impact is to have heavy and stiff outer FTACs along with large diameter bolts to absorb the impact energy so that it is not transmitted to the inner FTAC and the sealing integrity of the structure is not compromised
  • the present invention provides a solution for the aforementioned problems, by providing an outer FTAC according to claim 1, a wing of an aircraft according to claim 14 and an aircraft according to claim 15.
  • an outer FTAC according to claim 1 a wing of an aircraft according to claim 14 and an aircraft according to claim 15.
  • preferred embodiments of the invention are defined.
  • an outer fuel tank access cover (FTAC) of an aircraft comprising, an inner surface, an outer surface, the outer FTAC adapted for being used to cover the outer opening of a void area of a manhole for accessing the interior of a wing of an aircraft wherein the interior of the wing comprises a fuel tank characterized in that the outer FTAC comprises absorption means adapted for absorbing the impact energy due to an object impacting against the outer FTAC.
  • FTAC fuel tank access cover
  • the absorption of the impact energy is particularly carried out by plastic deformation of the outer FTAC provided by the invention.
  • the present invention approaches the technical problems described by providing an outer FTAC that intends to improve its sealing performance after an impact and is lighter with respect to current designs.
  • this approach reduces the energy transferred to the inner FTAC cover and surrounding wing.
  • the absorption of impact energy is achieved by converting the kinetic energy of the impacting fragment to work energy and heat by means of a plastic deformation of certain parts of the FTAC described.
  • a second aspect of the invention presents a wing of an aircraft comprising at least one fuel tank access comprising an outer FTAC according to the first aspect of the invention.
  • a last aspect of the invention presents an aircraft comprising a wing according to the second aspect of the invention.
  • FIG. 1A An embodiment of an aircraft is represented in figure 1A and its left wing is shown in figure 1B where the locations where the FTACs ( fig. 1C ) are located are shown.
  • figure 1D a sectional view of the inner area of the wing wherein the fuel tank (1) is located is represented.
  • figures 1D and 1E the relative position of the FTACs to the fuel tank (1) is shown.
  • the inner FTAC (3) is in the fuel tank (1) and it is sealed with fuel seals (17) to the lower wing skin (16).
  • the outer FTAC (4) is fixed to the lower wing skin (16) by means of a plurality of mounting holes peripherally distributed.
  • the fixing means (18), or fasteners, in an embodiment of the invention, are bolts.
  • the outer FTAC (4) comprises energy-absorption means which are at least one frangible line (5) located on the inner surface (4.1) of the outer FTAC (4) and calibrated for being ruptured once a predetermined level of energy due to an impact is reached on the inner surface (4.1) of the outer FTAC (4).
  • the frangible line is, in one embodiment of the invention, a v-shaped groove scratched on the inner surface (4.1) of the outer FTAC (4), as it can be seen on figure 2 .
  • the outer FTAC (4) is characterized in that the frangible line (5) is zigzag shaped.
  • the zigzag shape changes the load direction abruptly and creates stress risers aiding in the cracking process.
  • the outer FTAC (4) is characterized in that the frangible line (5) defines a closed region (6) within the inner surface (4.1) of the outer FTAC (4).
  • This frangible line (5) defining a closed region (6) advantageously creates a high stress riser that crack upon an impact event and, once the cracks propagate, the outer FTAC (4) plasticly deforms and therefore absorbs the impact energy.
  • deformable or crumble zones are created on the outer FTAC (4) so that it yields and plastically deforms. These deformation zones are created by the frangible line (5) and it is designed to break at certain energy ranges so that the outer FTAC (4) deforms and breaks in a controlled manner. The majority of the energy is absorbed by the outer FTAC (4) and advantageously it maintains sealing integrity of inner sealing of the outer FTAC (4).
  • the solution also reduces the amplitude of the propagation impact wave that is transferred to the inner FTAC (3), so that sealing integrity is fulfilled.
  • the outer FTAC (4) is characterized in that it comprises at least an extra frangible line (7).
  • the at least an extra frangible line (7) is, in one embodiment, inside the closed region (6).
  • the outer FTAC (4) is characterized in that the closed region (6) is ellipse-shaped and zigzagged, and the at least one extra frangible line (7) is zigzagged as it can be seen in figure 3A, 3B, 3C .
  • the outer FTAC (4) is characterized in that the closed region (6) is ellipse-shaped and stitched, and the at least one extra frangible line (7) is stitched as it can be seen in figure 3D, 3E, 3F .
  • the stitched feature of the frangible line must be understood as a succession of notches or small weakened areas having less thickness than the one of the outer FTAC (4).
  • the outer FTAC (4) is characterized in that it comprises a stiffener ring means (8) on the inner surface (4.1).
  • a stiffener ring means (8) on the inner surface (4.1).
  • the outer FTAC (4) is characterized in that the stiffener means (8) are a stiffener ring (8) surrounding all the frangible lines (5, 7) on the inner surface (4.1).
  • the stiffener ring (8) is part of the inner surface (4.1) of the outer FTAC (4) located in the interior perimeter defined by the line of bolts (18).
  • this stiffener ring (8) acts as a rip stop so the cracks do not propagate to the fasteners or bolts.
  • the fuel sealing integrity is maintained since the clamping force between the inner FTAC (3) and the outer FTAC (4) is maintained.
  • the outer FTAC (4) is made of metal.
  • the outer FTAC (4) is made of composite.
  • the outer FTAC (4) comprises absorption means which are at least one layer (10, 11) of a rigid material.
  • the absorption means are the outer FTAC (4) and it comprises at least one layer (10, 11) of a rigid material.
  • the absorption means are the outer FTAC (4) and the absorption means comprise a piece (9) made of a low density material forming the outer FTAC (4).
  • the absorption means are the outer FTAC (4), and comprise a piece (9) made of low density material sandwiched between two layers (10, 11) of a rigid material, as shown in figure 4.
  • Figure 4 even not being scaled, represents an outer FTAC (4) made of the two layers (10, 11) of a rigid material with a piece (9) of a low density material.
  • the outer FTAC (4) adapted for being fixed with the bolts (18) into the wing skin (16) in the aircraft.
  • the outermost layer (11) receives the impact
  • the piece (9) of a low density material absorbs the main percentage of the impact
  • the inner layer (10) provides rigidity to the whole structure.
  • the outer FTAC (4) is characterized in that the low density material is foam.
  • the outer FTAC (4) is characterized in that the two layers (10, 11) are aluminium layers, and the piece (9) is made of foam and sandwiched between the two layers (10, 11) of aluminium, as it can be seen in figure 4 .
  • the foam is Rohacell ® .
  • this embodiment yields weight saving opportunities.
  • the outer FTAC (4) is characterized in that the two layers (10, 11) are made of glass fibre reinforced plastic (GFRP).
  • GFRP glass fibre reinforced plastic
  • the solution having the two layers (10, 11) either made of aluminium or GFRP comprises the following advantages:
  • the solutions reduce the impact energy transferred to the outer FTAC (4) and surrounding wing skin (16).
  • the reduction of impact energy is achieved by converting the kinetic energy of the impacting fragment, for instance a tire fragment, into work-energy and heat by plastically deforming the outer FTAC (4).
  • an outer FTAC (4) is represented comprising a foam piece (9) between two layers (10, 11) of aluminium, the upper or inner layer (10) of aluminium being 2 mm thick and the lower or outermost layer (11) being 1mm thick.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Laminated Bodies (AREA)
  • Vibration Dampers (AREA)
  • Tires In General (AREA)

Abstract

The present invention describes an outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft. The invention belongs to the field of designing auxiliary pieces in the wings of aircraft to control the risk of impact against an inner FTAC when an impact occurs against the outer FTAC. This impact can be caused by a tire.

Description

    FIELD OF THE INVENTION
  • The present invention describes an outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft. The invention belongs to the field of designing auxiliary pieces in the wings of aircraft to control the risk of impact against an inner FTAC when an impact occurs against the outer FTAC. This impact can be caused by a tire.
    • BACKGROUND OF THE INVENTION
  • Manholes in an aircraft provide access to the fuel tank. Manholes comprise an inner fuel tank access cover (inner FTAC), an outer FTAC and a void area between the two covers. Fuel Tank Access Covers (FTACs) are mechanically fastened, with fasteners, such as bolts, and clamped against the aircraft wing skin to provide fuel tank access sealing. FTAC are designed to meet a wide array of requirements, some of them are: no fuel leaks, fire resistance, resistance to a tire impact, resistance to impacts resulting from an UERF (Uncontained Engine Rotor Failure), EMH/lightning strike, seal friction, and wing bending. The current design approach to address the resistance of the structure to an impact, for example, a tire impact, is to have heavy and stiff outer FTACs along with large diameter bolts to absorb the impact energy so that it is not transmitted to the inner FTAC and the sealing integrity of the structure is not compromised
  • The technical problem encountered in current solutions is that FTACs are too heavy. Another problem is the surrounding mounting structure is damaged which could create major repair issues.
  • Therefore, there is a need to find a solution for FTACs which
    decreases weight in an aircraft and which
    prevents the impact energy of an impact on the outer FTAC (4) to reach an inner FTAC (3) in an aircraft.
    prevent damage to the manhole mounting structure.
  • The mentioned prior art approach is seen in the patent US 4 291 816 A wherein a fluid tight closure for an aperture, adapted to form a fuel tank access door for an aircraft, and providing fail-safe features and resistance to lightning strikes is described
  • Other patent documents describing different solutions in aircrafts approaching absorption of impact energy and or designing FTAC and fuel tank access covers accomplishing the required characteristics taken into account in the state of the art are: EP 1 628 877 B1 , US 5,316,167 , US 2001/0010345 , US 2007/0207421 , US 2012/0217347 , US 4,291,816 .
    • DESCRIPTION OF THE INVENTION
  • The present invention provides a solution for the aforementioned problems, by providing an outer FTAC according to claim 1, a wing of an aircraft according to claim 14 and an aircraft according to claim 15. In dependent claims, preferred embodiments of the invention are defined.
  • In a first aspect of the invention, it is presented an outer fuel tank access cover (FTAC) of an aircraft comprising,
    an inner surface,
    an outer surface,
    the outer FTAC adapted for being used to cover the outer opening of a void area of a manhole for accessing the interior of a wing of an aircraft wherein the interior of the wing comprises a fuel tank
    characterized in that the outer FTAC comprises absorption means adapted for absorbing the impact energy due to an object impacting against the outer FTAC.
  • The absorption of the impact energy is particularly carried out by plastic deformation of the outer FTAC provided by the invention.
  • The present invention approaches the technical problems described by providing an outer FTAC that intends to improve its sealing performance after an impact and is lighter with respect to current designs.
  • Advantageously, this approach reduces the energy transferred to the inner FTAC cover and surrounding wing. The absorption of impact energy is achieved by converting the kinetic energy of the impacting fragment to work energy and heat by means of a plastic deformation of certain parts of the FTAC described.
  • The advantage of this solution over current designs is that the impact energy is mostly absorbed by the outer FTAC, minimizing the damage to the support structure, which ensures that sealing performance around the outer FTAC is fulfilled.
  • A second aspect of the invention presents a wing of an aircraft comprising at least one fuel tank access comprising an outer FTAC according to the first aspect of the invention.
  • A last aspect of the invention presents an aircraft comprising a wing according to the second aspect of the invention.
  • All the features described in this specification (including the claims, description and drawings) and/or all the steps of the described method can be combined in any combination, with the exception of combinations of such mutually exclusive features and/or steps.
    • DESCRIPTION OF THE DRAWINGS
  • These and other characteristics and advantages of the invention will become clearly understood in view of the detailed description of the invention which becomes apparent from a preferred embodiment of the invention, given just as an example and not being limited thereto, with reference to the drawings.
    • Figure 1A
    This figure represents an embodiment of an aircraft wherein the left wing is shown in black.
    Figure 1B
    This figure shows the locations of the wing of the aircraft shown in figure 1A where the FTACs are located.
    Figure 1C
    In this figure an embodiment of an outer FTAC according to the state of the art is represented.
    Figure 1D
    In this figure a sectional view of the inner area of the wing wherein the fuel tank (1) is located is represented. Besides, the relative position of the FTACs to the fuel tank (1) is shown. The different embodiments of the invention are located on the outer FTAC.
    Figure 1E
    In this figure a zoomed view of figure 1D is represented where the inner FTAC (3) and outer FTAC (4) are joined by means of bolts (18) and the inner FTAC (3) is shown to be sealed to the wing skin (16) with fuel seals (17).
    Figures 2A, 2B:
    These figures represent two views of an embodiment of the invention where a frangible line (5) is visible on the inner surface (4.1) of an outer FTAC (4). In figure 2B a particular embodiment is shown wherein the FTAC comprises a rip stop feature (8).
    Figures 3A, 3B, 3C, 3D, 3E, 3F:
    Various frangible line (5, 7) patterns are shown in figures 3A, 3B, 3C, 3D, 3E, 3F.
    Figure 4
    In this figure an embodiment of an outer FTAC is represented which comprises a foam core (9) between two layers (10, 11) of aluminium.
    Figure 5
    In this figure a comparative graphic is shown, wherein different levels of energy absorbed per second having different absorption means are represented.
    DETAILED DESCRIPTION OF THE INVENTION
  • Once the object of the invention has been outlined, specific non-limitative embodiments are described hereinafter.
  • An embodiment of an aircraft is represented in figure 1A and its left wing is shown in figure 1B where the locations where the FTACs (fig. 1C) are located are shown. In figure 1D a sectional view of the inner area of the wing wherein the fuel tank (1) is located is represented. Besides, in figures 1D and 1E the relative position of the FTACs to the fuel tank (1) is shown. The inner FTAC (3) is in the fuel tank (1) and it is sealed with fuel seals (17) to the lower wing skin (16). The outer FTAC (4) is fixed to the lower wing skin (16) by means of a plurality of mounting holes peripherally distributed. The fixing means (18), or fasteners, in an embodiment of the invention, are bolts.
  • In an embodiment of the invention, the outer FTAC (4) comprises energy-absorption means which are at least one frangible line (5) located on the inner surface (4.1) of the outer FTAC (4) and calibrated for being ruptured once a predetermined level of energy due to an impact is reached on the inner surface (4.1) of the outer FTAC (4). The frangible line is, in one embodiment of the invention, a v-shaped groove scratched on the inner surface (4.1) of the outer FTAC (4), as it can be seen on figure 2.
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that the frangible line (5) is zigzag shaped. Advantageously, the zigzag shape changes the load direction abruptly and creates stress risers aiding in the cracking process.
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that the frangible line (5) defines a closed region (6) within the inner surface (4.1) of the outer FTAC (4). This frangible line (5) defining a closed region (6) advantageously creates a high stress riser that crack upon an impact event and, once the cracks propagate, the outer FTAC (4) plasticly deforms and therefore absorbs the impact energy.
  • Another advantage provided by the solution proposed is that deformable or crumble zones are created on the outer FTAC (4) so that it yields and plastically deforms. These deformation zones are created by the frangible line (5) and it is designed to break at certain energy ranges so that the outer FTAC (4) deforms and breaks in a controlled manner. The majority of the energy is absorbed by the outer FTAC (4) and advantageously it maintains sealing integrity of inner sealing of the outer FTAC (4). Advantageously, the solution also reduces the amplitude of the propagation impact wave that is transferred to the inner FTAC (3), so that sealing integrity is fulfilled.
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that it comprises at least an extra frangible line (7). The at least an extra frangible line (7) is, in one embodiment, inside the closed region (6).
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that the closed region (6) is ellipse-shaped and zigzagged, and the at least one extra frangible line (7) is zigzagged as it can be seen in figure 3A, 3B, 3C.
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that the closed region (6) is ellipse-shaped and stitched, and the at least one extra frangible line (7) is stitched as it can be seen in figure 3D, 3E, 3F.
  • In the context of the present invention, the stitched feature of the frangible line must be understood as a succession of notches or small weakened areas having less thickness than the one of the outer FTAC (4).
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that it comprises a stiffener ring means (8) on the inner surface (4.1). Advantageously having a closed region (6) and stiffener ring means (8) makes the crack be contained within the stiffener ring means (8).
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that the stiffener means (8) are a stiffener ring (8) surrounding all the frangible lines (5, 7) on the inner surface (4.1). The stiffener ring (8) is part of the inner surface (4.1) of the outer FTAC (4) located in the interior perimeter defined by the line of bolts (18). Advantageously, this stiffener ring (8) acts as a rip stop so the cracks do not propagate to the fasteners or bolts. Advantageously, the fuel sealing integrity is maintained since the clamping force between the inner FTAC (3) and the outer FTAC (4) is maintained.
  • In an embodiment of the invention, the outer FTAC (4) is made of metal.
  • In an embodiment of the invention, the outer FTAC (4) is made of composite.
  • In a further embodiment of the invention the the outer FTAC (4) comprises absorption means which are at least one layer (10, 11) of a rigid material.
  • In a further embodiment of the invention the absorption means are the outer FTAC (4) and it comprises at least one layer (10, 11) of a rigid material.
  • In an embodiment of the invention the absorption means are the outer FTAC (4) and the absorption means comprise a piece (9) made of a low density material forming the outer FTAC (4).
  • In an embodiment of the invention the absorption means are the outer FTAC (4), and comprise a piece (9) made of low density material sandwiched between two layers (10, 11) of a rigid material, as shown in figure 4. Figure 4, even not being scaled, represents an outer FTAC (4) made of the two layers (10, 11) of a rigid material with a piece (9) of a low density material. The outer FTAC (4) adapted for being fixed with the bolts (18) into the wing skin (16) in the aircraft. Advantageously, in the event of an impact, the outermost layer (11) receives the impact, the piece (9) of a low density material absorbs the main percentage of the impact, and the inner layer (10) provides rigidity to the whole structure.
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that the low density material is foam.
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that the two layers (10, 11) are aluminium layers, and the piece (9) is made of foam and sandwiched between the two layers (10, 11) of aluminium, as it can be seen in figure 4. In one embodiment the foam is Rohacell®. Advantageously this embodiment yields weight saving opportunities.
  • In an embodiment of the invention, the outer FTAC (4) is characterized in that the two layers (10, 11) are made of glass fibre reinforced plastic (GFRP).
  • Advantageously, the solution having the two layers (10, 11) either made of aluminium or GFRP comprises the following advantages:
    • no complex manufacturing,
    • aerodynamic features, and.
    • low weight
  • The solutions reduce the impact energy transferred to the outer FTAC (4) and surrounding wing skin (16). The reduction of impact energy is achieved by converting the kinetic energy of the impacting fragment, for instance a tire fragment, into work-energy and heat by plastically deforming the outer FTAC (4).
    • Exemplary embodiment
  • A detailed structural analysis and testing have been performed testing the outer FTAC (4) of the invention which received the impact of an aircraft tire fragment. Various frangible lines (5) patterns, some of them shown in figures 3A, 3B, 3C, 3D, 3E, 3F, have been analyzed using structural analysis software to determine the different energy absorption characteristics for each solution.
  • In figure 4 an outer FTAC (4) is represented comprising a foam piece (9) between two layers (10, 11) of aluminium, the upper or inner layer (10) of aluminium being 2 mm thick and the lower or outermost layer (11) being 1mm thick.
  • The embodiment of an outer FTAC (4) comprising a foam core (9) between the two layers of aluminium (10, 11) analytically shows the major absorbed impact energy. In figure 5 the absorbed impact energy, in joules (axis Y represents Energy in joules) per second (axis X represents time). The legend of such figure is as follows:
    • (12): Absorbed tire impact energy by an outer FTAC comprising a zigzagged frangible line as shown in figure 7.
    • (13): Absorbed tire impact energy by an outer FTAC (4) comprising a stitched frangible line (5) as shown in figure 6.
    • (14): Absorbed tire impact energy by an outer FTAC (4) comprising a foam piece (9) between two layers (10, 11) of aluminium, as shown in figure 4.
    • (15) Absorbed tire impact energy by an outer FTAC (4) comprising a frangible ellipse and zigzagged line (5) and a straight zigzagged frangible line (7), as shown in figure 3A.
  • The rising conclusions are:
    • the zigzag pattern provides better results than the stitched pattern,
    • the closed ellipse (5) also provides better results than having a single frangible line (7),
    • the best performance is provided by a foam piece (9) between two layers (10, 11) of aluminium, as shown in figure 4.

Claims (15)

  1. Outer fuel tank access cover (FTAC) (4) of an aircraft comprising,
    an inner surface (4.1),
    an outer surface (4.2),
    the outer FTAC adapted for being used to cover the outer opening of a void area (2) of a manhole for accessing the interior of a wing of an aircraft wherein the interior of the wing comprises a fuel tank (1),
    characterized in that the outer FTAC comprises absorption means adapted for absorbing the impact energy due to an object impacting against the outer FTAC (4).
  2. Outer FTAC (4) according to claim 1 characterized in that the absorption means are at least one frangible line (5) located on the inner surface (4.1) of the outer FTAC (4) and calibrated for being ruptured once a predetermined level of energy due to an impact is reached.
  3. Outer FTAC (4) according to claim 2 characterized in that the frangible line (5) is zigzag shaped.
  4. Outer FTAC (4) according to claims 2 or 3 characterized in that the frangible line (5) defines a closed region (6) within the inner surface (4.1) of the outer FTAC (4).
  5. Outer FTAC (4) according to any of the preceding claims characterized in that it comprises at least an extra frangible line (7).
  6. Outer FTAC (4) according to claims 4 or 5 characterized in that the closed region (6) is ellipse-shaped and the at least one extra frangible line (7) is zigzaged.
  7. Outer FTAC (4) according to any of the preceding claims characterized in that it comprises a stiffener means (8).
  8. Outer FTAC (4) according to claim 7 characterized in that the stiffener means (8) is a stiffener ring (8) surrounding all the frangible lines (5, 7) on the inner surface (4.1) and it is located within the interior perimeter defined by the line of bolts (18).
  9. Outer FTAC (4) according to any of the preceding claims characterized in that the outer FTAC (4) is made of metal.
  10. Outer FTAC (4) according to claim 1 characterized in that the absorption means comprise at least one layer (10, 11) of a rigid material in the outer FTAC (4).
  11. Outer FTAC (4) according to claim 1 characterized absorption means comprise at least one piece (9) made of a low density material.
  12. Outer FTAC (4) according to claims 10 and 11 characterized in that the piece (9) made of a low density material is sandwiched between the two layers (10, 11) of a rigid material.
  13. Outer FTAC (4) according to claim 12 characterized in that the two layers (10, 11) are aluminium layers and the piece (9) made of a low density material is made of foam.
  14. Wing of an aircraft comprising at least one fuel tank access comprising an outer FTAC (4) according to any of the preceding claims.
  15. Aircraft comprising a wing according to claim 14.
EP12382523.4A 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover Not-in-force EP2746150B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP12382523.4A EP2746150B1 (en) 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover
EP15156088.5A EP2902313B1 (en) 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover
US14/136,725 US20140191085A1 (en) 2012-12-21 2013-12-20 Outer fuel tank access cover, wing and aircraft
CN201310716752.3A CN103879548A (en) 2012-12-21 2013-12-23 Outer fuel tank access cover, wing and aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12382523.4A EP2746150B1 (en) 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover

Related Child Applications (2)

Application Number Title Priority Date Filing Date
EP15156088.5A Division-Into EP2902313B1 (en) 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover
EP15156088.5A Division EP2902313B1 (en) 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover

Publications (2)

Publication Number Publication Date
EP2746150A1 true EP2746150A1 (en) 2014-06-25
EP2746150B1 EP2746150B1 (en) 2017-04-05

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Application Number Title Priority Date Filing Date
EP12382523.4A Not-in-force EP2746150B1 (en) 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover
EP15156088.5A Not-in-force EP2902313B1 (en) 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP15156088.5A Not-in-force EP2902313B1 (en) 2012-12-21 2012-12-21 Outer fuel tank access cover, wing and aircraft comprising such a cover

Country Status (3)

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US (1) US20140191085A1 (en)
EP (2) EP2746150B1 (en)
CN (1) CN103879548A (en)

Cited By (3)

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Publication number Priority date Publication date Assignee Title
WO2017072460A1 (en) 2015-10-28 2017-05-04 Aviacomp Door for accessing the fuel tank or a dry zone of an aircraft
WO2017072459A1 (en) 2015-10-28 2017-05-04 Aviacomp Access door to the fuel tank or dry zone of an aircraft
WO2022057115A1 (en) * 2020-09-15 2022-03-24 中国商用飞机有限责任公司北京民用飞机技术研究中心 Airplane wing fuel tank access cover and structure of peripheral area of access cover

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022211424B3 (en) * 2022-10-27 2024-01-04 Airbus Defence and Space GmbH Device for creating a stiffened area on an external structure of an aircraft for the subsequent provision of service access if necessary, and method for producing and using such a service access

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US5316167A (en) 1992-12-23 1994-05-31 United Technologies Corporation Pressure resistant fuel tank closure
US20010010345A1 (en) 2000-01-29 2001-08-02 Clifford William Simon Method of improving the crashworthiness of an aircraft
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EP1628877B1 (en) 2003-05-30 2009-09-02 Politecnico Di Milano Crashworthiness structure and method
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US4291816A (en) 1980-07-09 1981-09-29 Canadair Limited Fuel tank access door for aircraft
US4530443A (en) * 1983-11-10 1985-07-23 The Boeing Company Unitary access panel for aircraft fuel tanks
US5316167A (en) 1992-12-23 1994-05-31 United Technologies Corporation Pressure resistant fuel tank closure
US20010010345A1 (en) 2000-01-29 2001-08-02 Clifford William Simon Method of improving the crashworthiness of an aircraft
EP1628877B1 (en) 2003-05-30 2009-09-02 Politecnico Di Milano Crashworthiness structure and method
US20070207421A1 (en) 2006-02-23 2007-09-06 Heeter Russell J Method and system for electrical bonding of fuel tank penetrations
US20090166473A1 (en) * 2007-12-27 2009-07-02 Airbus Espana, S.L. Optimized aircraft manhole
US20120217347A1 (en) 2011-02-24 2012-08-30 Airbus Operations Limited aircraft fuel tank access cover and an aircraft fuel tank

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017072460A1 (en) 2015-10-28 2017-05-04 Aviacomp Door for accessing the fuel tank or a dry zone of an aircraft
WO2017072459A1 (en) 2015-10-28 2017-05-04 Aviacomp Access door to the fuel tank or dry zone of an aircraft
FR3043064A1 (en) * 2015-10-28 2017-05-05 Aviacomp ACCESS DOOR TO THE FUEL TANK OR A DRY ZONE OF AN AIRCRAFT
WO2022057115A1 (en) * 2020-09-15 2022-03-24 中国商用飞机有限责任公司北京民用飞机技术研究中心 Airplane wing fuel tank access cover and structure of peripheral area of access cover
EP3998193A4 (en) * 2020-09-15 2022-10-26 Beijing Aeronautical Science & Technology Research Institute,Commercial Aircraft Corporation of China FUEL ACCESS CAP FOR AIRCRAFT WINGS AND STRUCTURE OF THE PERIPHERAL AREA OF AN ACCESS CAP

Also Published As

Publication number Publication date
CN103879548A (en) 2014-06-25
EP2746150B1 (en) 2017-04-05
EP2902313A1 (en) 2015-08-05
US20140191085A1 (en) 2014-07-10
EP2902313B1 (en) 2017-05-10

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